CN106945852B - A kind of space load butt-joint locking and unlock interface arrangement of meeting an urgent need - Google Patents
A kind of space load butt-joint locking and unlock interface arrangement of meeting an urgent need Download PDFInfo
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- CN106945852B CN106945852B CN201710139641.9A CN201710139641A CN106945852B CN 106945852 B CN106945852 B CN 106945852B CN 201710139641 A CN201710139641 A CN 201710139641A CN 106945852 B CN106945852 B CN 106945852B
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- 239000003638 chemical reducing agent Substances 0.000 claims abstract description 17
- 238000003032 molecular docking Methods 0.000 claims abstract description 17
- 238000010008 shearing Methods 0.000 claims description 19
- 230000007246 mechanism Effects 0.000 claims description 15
- 241000826860 Trapezium Species 0.000 claims description 12
- 238000000034 method Methods 0.000 claims description 5
- 238000012544 monitoring process Methods 0.000 claims description 3
- 230000004992 fission Effects 0.000 abstract description 44
- 230000033001 locomotion Effects 0.000 description 4
- 230000008569 process Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000001681 protective effect Effects 0.000 description 2
- 230000001960 triggered effect Effects 0.000 description 2
- 230000005611 electricity Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/646—Docking or rendezvous systems
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Abstract
The invention discloses a kind of space load butt-joint locking and emergency unlock interface arrangements, belong to space application equipment technical field, it includes drive end and Partner, are fixedly connected respectively with exposure load and spacecraft cabin exposure platform；By the master positioning pin on drive end and the cooperation with the master positioning hole on Partner, robotic arm manipulation exposure load is guided to be docked on position to be installed；Lead screw is driven by the motor reducer on drive end, and then seperated rack A main body, rack A, rack B main body and rack B fission is driven to realize along the mode that guide shaft moves to the rigid locking for exposing load；And when butt-joint locking device can not be unlocked by electronic mode, by the emergency release fixation kit on operation drive end, the mechanical release to drive end and Partner is manually completed；The present invention is capable of auxiliary mechanical arm realization exposure load and the guidance of aircraft cabin positions docking, passively captures, actively tightening, rigid locking, manual unlocking.
Description
Technical field
The invention belongs to space application equipment technical fields, and in particular to a kind of space load butt-joint locking and solution of meeting an urgent need
Lock interface device.
Background technique
The spacecrafts such as space station, manned spaceship arrange a large amount of exposure load test stabilization platforms in cabin outer wall to extend
The exposure experimental ability of spacecraft.International space station has used the load butt-joint locking interface arrangement branch of diversified forms at present
Hold exposed experimental duties.
But for exposing load out of my cabin and exposing platform out of my cabin, butt-joint locking interface arrangement in the prior art cannot be certainly
Exposed load, the degree of automation be not high out of my cabin, high to the operational capacity requirement of spacefarer or mechanical arm, mechanism is complicated for dynamic capture,
Maintenanceability is poor, reliability is lower.
Summary of the invention
In view of this, the object of the present invention is to provide a kind of space load butt-joint locking and emergency unlock interface arrangement,
It docked by the guidance positioning that the attachment device can be realized exposed load and spacecraft cabin exposure platform, passively caught
It obtains, actively tightening, rigid locking, manual unlocking and emergency unlock, to be that will expose load and be installed on aircraft to set out of my cabin
Position provides technical support.
The present invention is achieved through the following technical solutions:
A kind of space load butt-joint locking and unlock interface arrangement of meeting an urgent need, including drive end and Partner, respectively and cruelly
Dew load is fixedly connected with spacecraft cabin exposure platform；
The drive end includes: bottom plate, guide shaft, lead screw, rack A main body, rack A fission, rack B main body, rack B points
Body, emergency release fixation kit, motor reducer, master positioning pin, bulb shear pin, auxiliary positioning pin, rigid locking mechanism, list
To acquisition equipment and shell；
Lead screw and two guide shafts are parallel to each other is mounted on bottom plate, and lead screw is located between two guide shafts；The one of lead screw
End is machined with the tool interface for rotating manually, and the other end is coaxially fixed with motor reducer；Two sections of rotations are machined on lead screw
To opposite screw thread, screw pair is formed with the threaded hole among rack A main body and rack B main body respectively；On each guide shaft
It is separately installed with the rack A fission that can be moved along its axis and rack B is seperated；Rack A main body is solid by two emergency releases
Determine component respectively it is seperated with two rack A connection, rack B main body by another two emergency release fixation kit respectively with two machines
Frame B fission connection, wherein the butt-joint locking device that emergency release fixation kit is used for after locking can not be by directly driving silk
When the mode of thick stick unlocks, emergency release fixation kit is directly driven by tool and is unlocked；
Two master positioning pins, two bulb shear pins and an auxiliary positioning pin are separately fixed on bottom plate；Four shells
It is separately mounted on two rack A fissions and two rack B fissions；The pilot hole of rectangle, the pilot hole are machined on shell
In a side be grouped as by chamfered portion and planar portions；List is mounted on each rack A fission and each rack B fission
To acquisition equipment and rigid locking mechanism；Rigid locking mechanism is for the locking after drive end and Partner docking；
The Partner includes: framework and multi-functional pin；
Master positioning hole, a shearing perforation, a kidney-shaped shearing perforation and an auxiliary positioning hole there are two being set in the framework；
When drive end is docked with Partner, the master positioning hole and master positioning pin cooperate, and shearing perforation and kidney-shaped shearing perforation are respectively with two
A bulb shear pin cooperation, auxiliary positioning hole and auxiliary positioning pin cooperate；
Four multi-functional pins are separately mounted on the side wall at four angles of framework, wherein multi-functional pin include: plane frame plate and
The locking of drive end and Partner is realized in the latch segment being fixed on plane frame plate, latch segment and the cooperation of rigid locking mechanism；Institute
Stating plane frame plate is right-angled trapezium plate, and the bottom circle of position column pin-shaped structure of the right-angled trapezium plate is capture portion, when actively
When end is docked with Partner, capture portion is first matched with unidirectional acquisition equipment, is positioned to the docking；Right-angled trapezium plate
Bevel edge is tightening part, and the chamfered portion for the pilot hole with shell cooperates, and the upper bottom edge of right-angled trapezium plate is height limit
Part, the planar section for the pilot hole with shell cooperate；
Wherein, the emergency release fixation kit includes: locking driving screw rod, screw thread compact heap, rotatably compresses block, screw rod
Locking cap and rigid pins；One end of the locking driving screw rod is equipped with external screw thread, and the other end is equipped with tool operation interface；The spiral shell
The center of line compact heap is equipped with threaded hole；
Connection relationship between emergency release fixation kit is seperated with rack A main body and rack A are as follows: screw thread compact heap is fixed
Cooperate in rack A main body, and through the external screw thread of its threaded hole and locking driving screw rod one end；It rotatably compresses block and passes through connection
Frame is fixed on rack A fission, and is fixed on locking driving screw flight end by screw rod locking cap, locking driving screw rod
Tool operation interface protrudes from the side of bottom plate；Screw thread compact heap passes through rigid pin connection with block is rotatably compressed；
Emergency release fixation kit is connected using above-mentioned identical connection type is seperated with rack B main body and rack B.
Further, drive end further includes microswitch, and microswitch is mounted on the side of bottom plate, and the touching of microswitch
Leaven dough it is concordant with the upper surface of drive end, for monitoring the docking surface contact state of drive end and Partner, when drive end and by
When the docking face contact of moved end, microswitch is triggered, shows that drive end and Partner complete docking.
Further, two master positioning pins and two bulb shear pins are symmetrically distributed in the two sides of lead screw respectively.
Further, the master positioning pin is made of cylindrical section and tip；
The master positioning hole is made of bellmouth and cylindrical hole two parts, and wherein bellmouth is used for the tip with master positioning pin
Cooperation, cylindrical hole are used to cooperate with the cylindrical section of master positioning pin.
Further, the drive end further includes blind-mating connector plug, and two blind-mating connector plugs are fixed on bottom plate
On, and it is symmetrically distributed in the two sides of rack A main body；The Partner further includes blind-mating connector socket, blind-mating connector socket
It is mounted in framework, when Partner is docked with drive end, for being connect with blind-mating connector plug.
The utility model has the advantages that (1) present invention is capable of the guidance positioning pair of auxiliary mechanical arm realization exposure load and aircraft cabin
It connects, passively capture, actively tightening, rigid locking, manual unlocking, to be that will expose load and be installed on aircraft to set position out of my cabin
Offer technical support is provided.
(2) present invention passes through the master on master positioning pin, bulb shear pin and the auxiliary positioning pin and Partner on drive end
Location hole, shearing perforation, kidney-shaped shearing perforation and the cooperation in auxiliary positioning hole, guidance robotic arm manipulation exposure load are docked to be installed
On position.
(3) present invention realizes the capture to exposure load by unidirectional acquisition equipment in docking operation automatically, guarantees connection
The safety of process.
(4) present invention drives lead screw by motor reducer, and then drives rack A main body, rack A fission, rack B main body
The tightening to exposure load is realized along the mode that guide shaft moves with rack B fission, the electric connector of exposure load is plugged, to sudden and violent
Reveal the rigid locking of load and reliable locking.
It (5), can be by space flight when butt-joint locking device can not be unlocked independently in such a way that motor reducer drives lead screw
The tool interface that member goes out lead screw one end that cabin is located at drive end by operation manually completes the mechanical solution to drive end and Partner
The operation that lock and electric connector are extracted.
(6) when interface arrangement can not be unlocked independently by electronic mode, and manual operation drive end lead screw can not be passed through
When unlock, cabin can be gone out by spacefarer by the locking on operation emergency release fixation kit and drives screw rod, is manually completed to actively
The operation that the mechanical release and electric connector of end and Partner are extracted.
Detailed description of the invention
Fig. 1 is structure composition figure of the invention.
Fig. 2 is the structure composition figure of drive end of the invention.
Fig. 3 is the structure composition figure of emergency release fixation kit of the invention.
Fig. 4 is schematic diagram of housing structure of the invention.
Fig. 5 is the structure composition figure of Partner of the invention.
Fig. 6 is multi-functional latch structure schematic diagram of the invention.
Fig. 7 is locking state figure of the invention.
Wherein, 1- microswitch, 2- bottom plate, 3- master positioning pin, 4- bulb shear pin, 5- guide shaft, 6- rigid locking mechanism,
The unidirectional acquisition equipment of 7-, 9- rack B is seperated, 10- protective cover, and 11- rack A is seperated, 12- emergency release fixation kit, and 13- is automatically controlled
Box, 14- lead screw, 15- auxiliary positioning pin, 17- bearing block, 18- rack A main body, 19- blind-mating connector plug, 20- rack B master
Body, 21- motor reducer, the multi-functional pin of 22-, 23- master positioning hole, 24- shearing perforation, 25- kidney-shaped shearing perforation, 26- framework, 27-
Blind-mating connector socket, 28- socket support, 29- electric connector bracket, 30- electric connector, 31- auxiliary positioning hole, 32- shell,
36- rigid pins I, 37- rotatably compress block I, 38- screw rod locking cap I, 39- locking driving screw rod I, 40- screw thread compact heap I, 41-
Height limit part, 42- tighten part, 43- capture portion, 45- latch segment, 100- exposure load, 200- drive end, 300- quilt
Moved end.
Specific embodiment
The present invention will now be described in detail with reference to the accompanying drawings and examples.
The present invention provides a kind of space load butt-joint locking and emergency unlock interface arrangements, referring to attached drawing 1, including master
Moved end 200 and Partner 300 are fixedly connected with exposure load and spacecraft cabin exposure platform respectively, pass through drive end
200 and Partner 300 butt-joint locking, and then realize exposure load and spacecraft cabin exposure platform butt-joint locking；
Referring to attached drawing 2, the drive end 200 include: microswitch 1, bottom plate 2, guide shaft 5, lead screw 14, rack A main body 18,
Rack A fission 11, rack B main body 20, rack B fission 9, emergency release fixation kit 12, motor reducer 21, master positioning pin 3,
Bulb shear pin 4, auxiliary positioning pin 15, blind-mating connector plug 19, rigid locking mechanism 6, unidirectional acquisition equipment 7, protective cover
10, electric-controlled box 13, bearing block 17 and shell 32；
On a base plate 2, and lead screw 14 is located between two guide shafts 5 for lead screw 14 and the installation parallel to each other of two guide shafts 5；Silk
One end of thick stick 14 protrudes from 2 side of bottom plate, and is machined with the tool interface for rotating manually in the end end face, and the other end is coaxial
It is fixed with motor reducer 21；Two sections of oppositely oriented screw threads are machined on lead screw 14, respectively with rack A main body 18 and rack B
Threaded hole among main body 20 forms screw pair；It is separately installed with rack A fission 11 on each guide shaft 5 and rack B is seperated
9, rack A 11 and rack B of fission fission 9 can be moved axially along guide shaft 5；Rack A main body 18 passes through two emergency releases
Fixation kit 12 respectively divided by another two emergency release fixation kit 12 by 11 connection seperated with two rack A, rack B main body 20
9 connection not seperated with two rack B；Wherein, the butt-joint locking device that emergency release fixation kit 12 is used for after locking can not
When being unlocked by way of directly driving lead screw 14, emergency release fixation kit 12 is directly driven by tool and is unlocked；
Two master positioning pins, 3, two bulb shear pins 4 and an auxiliary positioning pin 15 are separately fixed at bottom plate 2 and are equipped with
Installation interface, wherein two master positioning pins 3 and two bulb shear pins 4 are symmetrically distributed in the two sides of lead screw 14 respectively；
Master positioning pin 3 is made of cylindrical section and tip；
Two blind-mating connector plugs 19 are fixed on a base plate 2, and are symmetrically distributed in the two sides of rack A main body 18, protect
10 cover of cover is outside blind-mating connector plug 19；Electric-controlled box 13 is fixed on a base plate 2,21 electricity of electric-controlled box 13 and motor reducer
Gas connection, for controlling the rotation of motor reducer 21；
Four shells 32 are separately mounted on two rack A fissions 11 and two rack B fissions 9；Referring to attached drawing 4, shell
The pilot hole of rectangle is machined on 32, a side in the pilot hole is grouped as by chamfered portion and planar portions；
Unidirectional acquisition equipment 7 and rigid locking mechanism are mounted on each rack A fission 11 and each rack B fission 9
6；Rigid locking mechanism 6 is for the locking after drive end 200 and the docking of Partner 300；Location status indicating mechanism is mounted on bottom
On plate 2, it is used to indicate the location status of rack A fission 11；
Microswitch 1 is mounted on the side of bottom plate 2, and the triggering face of microswitch 1 is concordant with the upper surface of drive end；It is micro-
Dynamic switch 1 is for monitoring the docking surface contact state of drive end 200 and Partner 300, when drive end 200 and Partner 300
When docking face contact, microswitch 1 is triggered, shows that drive end and Partner complete docking；
Wherein, referring to attached drawing 3, the emergency release fixation kit 12 includes: locking driving screw rod 39, screw thread compact heap
40, block 37, screw rod locking cap 38 and rigid pins 36 are rotatably compressed；One end of the locking driving screw rod 39 is equipped with external screw thread, separately
One end is equipped with tool operation interface；40 side of screw thread compact heap is equipped with shearing perforation, and center is equipped with threaded hole；The rotation pressure
Tight 37 side of block is equipped with mounting hole；
Screw thread compact heap 40 is fixed in rack A main body 18, and passes through the threaded hole at its center and locking driving screw rod 39
The external screw thread of one end cooperates；It rotatably compresses block 37 to be fixed on rack A fission 11 by connection frame, and passes through screw rod locking cap 38
It is fixed on the end of thread of locking driving screw rod 39, the tool operation interface of locking driving screw rod 39 protrudes from the side of bottom plate 2, side
Just it operates；The shearing perforation of screw thread compact heap 40 is opposite with the mounting hole for rotatably compressing block 37, and passes through rigid pins 36 for screw thread pressure
Tight block 40 is connected with block 37 is rotatably compressed, and is guaranteed when emergency release fixation kit 12 does not work, screw thread compact heap 40 and rotation
The relative position of compact heap 37 remains unchanged；When emergency release fixation kit 12 works, pass through the work of locking driving screw rod 39
Have operation interface rotation lock and drives screw rod 39, since screw thread compact heap 40 remains stationary, locking driving screw rod 39 and rotation
Turn compact heap 37 to move axially along locking driving screw rod 39, while rigid pins 36 fall off, and then drive rack A fission 11 along guide shaft
5 is mobile；
When screw thread compact heap 40 is fixed on rack B fission 9, turns compact heap 37 by connection frame and be fixed on rack B main body
When on 20, drives screw rod 39 to be able to drive rack B fission 9 by rotation lock and moved along guide shaft 5；
Referring to attached drawing 5, the Partner 300 includes: framework 26, multi-functional pin 22, blind-mating connector socket 27, socket branch
Frame 28, electric connector 30 and electric connector bracket 29；
Set in the framework 26 there are two 23, one, master positioning hole shearing perforation, 24, kidney-shaped shearing perforations 25 and one it is auxiliary
Help location hole 31；Two master positioning holes 23 are made of bellmouth and cylindrical hole two parts, and wherein bellmouth is used for and leads
The tip of the master positioning pin 3 of moved end 200 cooperates, and in a big way directs into master positioning pin 3 in cylindrical hole, subsequent drive end
The cylindrical hole in the 300 master positioning hole 23 of cylindrical section and Partner of 200 master positioning pin 3 cooperates to correct the posture of master positioning pin 3；
Shearing perforation 24 and kidney-shaped shearing perforation 25 are used to cooperate with two bulb shear pins 4, and auxiliary positioning hole 31 is by kidney-shaped bellmouth and waist
Shape cylindrical hole two parts composition, kidney-shaped bellmouth are formed by connecting by two bellmouths at a distance of set distance by flat segments, waist
Shape cylindrical hole is formed by connecting by two cylindrical holes at a distance of set distance by flat segments；Auxiliary positioning hole 31 is used for fixed with auxiliary
Position pin 15 cooperates；
Blind-mating connector socket 27 is mounted in framework 26 by socket support 28, right in Partner 300 and drive end 200
When connecing, for being connect with blind-mating connector plug 19；Electric connector 30 is mounted on 26 side of framework by electric connector bracket 29,
Electric connector 30 and blind-mating connector socket 27 are electrically connected, for powering to blind-mating connector socket 27；
Four multi-functional pins 22 are separately mounted on the side wall at 26 4 angles of framework, wherein referring to attached drawing 6, multi-functional pin
22 include: plane frame plate and the latch segment 45 that is fixed on plane frame plate, and master is realized in latch segment 45 and the cooperation of rigid locking mechanism 6
The locking of moved end 200 and Partner 300；The plane frame plate is right-angled trapezium plate, the bottom circle of position of the right-angled trapezium plate
Column pin-shaped structure is capture portion 43, when drive end 200 is docked with Partner 300, capture portion 43 and unidirectional acquisition equipment
7 first match, and position to the docking；The bevel edge of right-angled trapezium plate is tightening part 42, for the pilot hole with shell 32
Chamfered portion cooperation, the upper bottom edge of right-angled trapezium plate is height limit part 41, the plane for the pilot hole with shell 32
Part cooperates.
Working principle: referring to attached drawing 7, when exposure load 100 is fixed to drive end 200, Partner 300 is fixed on space
On aircraft cabin exposure platform；Or when exposure load 100 is fixed to Partner 300, drive end 200 is fixed on space and flies
On row device cabin exposure platform；
It is powered on for drive end 200, motor reducer 21 is controlled by electric-controlled box 13 and is worked, driving lead screw 14 rotates, and passes through
The screw pair pushes rack A main body 18, rack A fission 11, rack B main body 20, rack B fission 9 to move to initial bit
It sets；
Make two master positioning pins 3 and an auxiliary positioning pin on drive end 200 by robotic arm manipulation exposure load 100
15 enter on Partner 300 in two master positioning holes 23 and an auxiliary positioning hole 31, during entrance on Partner 200
Four multi-functional pins 22 capture portion 43 on drive end 300 be located at rack B seperated 9 on and rack A fission 11 on list
It is matched to acquisition equipment 7, exposure load 100 is captured；
It drives lead screw 14 to rotate by the motor reducer 21 that electric-controlled box 13 controls drive end 300, passes through screw pair
Two end motions of rack A main body 18, rack A fission 11, rack B main body 20, rack B fission 9 to guide shaft 5 are pushed, are now placed in
Function more than four on the pilot hole chamfered portion and Partner 200 of four shells 32 on rack B fission 9 and on rack A fission 11
The tightening part 42 of energy pin 22 cooperates, by drive end 300 and the close fitting of the tightening of Partner 200, two bulbs of drive end 300
Shear pin 4 respectively enters the shearing perforation 24 and kidney-shaped shearing perforation 25 of Partner 200, at this time the phase of drive end 300 and Partner 200
Position is accurately corrected；
It continues through electric-controlled box 13 and controls the driving of motor reducer 21 rotation of lead screw 14 in drive end 300, pass through lead screw spiral shell
Female secondary promotion rack A main body 18, rack A fission 11, rack B main body 20, rack B fission 9 continue two end motions to guide shaft 5,
Four on the pilot hole planar section and Partner 200 of four shells 32 on rack B fission 9 and on rack A fission 11
The height limit part 41 of multi-functional pin 22 cooperates, and limits the relative position of drive end 300 and Partner 200, while two
A blind-mating connector plug 19 enters two blind-mating connector sockets 27 on Partner 200；
It continues through electric-controlled box 13 and controls the driving of motor reducer 21 rotation of lead screw 14 in drive end 300, pass through lead screw spiral shell
Female secondary promotion rack A main body 18, rack A fission 11, rack B main body 20, rack B fission 9 continue two end motions to guide shaft 5,
Four on the rigid fastening devices 6 and Partner 200 in four shells 32 on rack B fission 9 and on rack A fission 11
The lock portion 45 of multi-functional pin 22 locks；
At this point, rack A main body 18, rack A fission 11, rack B main body 20, rack B fission 9 move and stop in place；Actively
End 300 completes butt-joint locking with Partner 200 and electric connector is connect；
Drive end 300 is opposite with locking process with the unlocking process of Partner 200；
Butt-joint locking device after locking can not directly drive lead screw by control electric-controlled box 13 and motor reducer 21
When 14 mode unlocks, the locking driving screw rod 39 that can be directly driven by tool on emergency release fixation kit 12 is rotated,
And then rack B fission 9, rack A fission 11 is pushed to complete drive end until moving to unlocked position to the intermediary movements of guide shaft 5
300 and Partner 200 unlock.
In conclusion the above is merely preferred embodiments of the present invention, being not intended to limit the scope of the present invention.
All within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in of the invention
Within protection scope.
Claims (5)
1. a kind of space load butt-joint locking and emergency unlock interface arrangement, which is characterized in that including drive end and Partner,
It is fixedly connected respectively with exposure load and spacecraft cabin exposure platform；
The drive end includes: bottom plate (2), guide shaft (5), lead screw (14), rack A main body (18), rack A seperated (11), rack B
Main body (20), rack B seperated (9), emergency release fixation kit (12), motor reducer (21), master positioning pin (3), bulb are cut
Cut pin (4), auxiliary positioning pin (15), rigid locking mechanism (6), unidirectional acquisition equipment (7) and shell (32)；
Lead screw (14) and two guide shafts (5) are parallel to each other is mounted on bottom plate (2), and lead screw (14) is located at two guide shafts (5)
Between；One end of lead screw (14) is machined with the tool interface for rotating manually, and the other end is coaxially fixed with motor reducer
(21)；Two sections of oppositely oriented screw threads are machined on lead screw (14), respectively and in rack A main body (18) and rack B main body (20)
Between threaded hole formed screw pair；It is seperated that the rack A that can be moved along its axis is separately installed on each guide shaft (5)
(11) and rack B is seperated (9)；Rack A main body (18) is divided with two rack A respectively by two emergency release fixation kits (12)
Body (11) connection, rack B main body (20) pass through another two emergency release fixation kit (12) respectively (9) seperated with two rack B
Connection, wherein emergency release fixation kit (12) be used for when locking after the butt-joint locking and emergency unlock interface arrangement without
When method is unlocked by way of directly driving lead screw (14), emergency release fixation kit (12) is directly driven by tool and is solved
Lock；
Two master positioning pins (3), two bulb shear pins (4) and an auxiliary positioning pin (15) are separately fixed on bottom plate (2)；
Four shells (32) are separately mounted on two rack A seperated (11) and two rack B seperated (9)；Shell is machined on (32)
The pilot hole of rectangle, a side in the pilot hole are grouped as by chamfered portion and planar portions；Each rack A is seperated (11)
Unidirectional acquisition equipment (7) and rigid locking mechanism (6) are mounted on on each rack B seperated (9)；Rigid locking mechanism (6)
For the locking after drive end and Partner docking；
The Partner includes: framework (26) and multi-functional pin (22)；
Master positioning hole (23), a shearing perforation (24), a kidney-shaped shearing perforation (25) and one there are two being set on the framework (26)
A auxiliary positioning hole (31)；When drive end is docked with Partner, the master positioning hole (23) and master positioning pin (3) cooperate, and cut
Cut hole (24) and kidney-shaped shearing perforation (25) cooperate with two bulb shear pins (4) respectively, auxiliary positioning hole (31) and auxiliary positioning
Sell (15) cooperation；
Four multi-functional pins (22) are separately mounted on the side wall at (26) four angles of framework, wherein multi-functional pin (22) includes: flat
Face frame plate and the latch segment being fixed on plane frame plate (45), latch segment (45) and rigid locking mechanism (6) cooperation are realized actively
The locking at end and Partner；The plane frame plate is right-angled trapezium plate, and the bottom of the right-angled trapezium plate is the pin-shaped knot of cylinder
Structure is capture portion (43) that when drive end is docked with Partner, capture portion (43) is first matched with unidirectional acquisition equipment (7),
The docking is positioned；The bevel edge of right-angled trapezium plate is tightening part (42), for oblique with the pilot hole of shell (32)
Face distribution is closed, and the upper bottom edge of right-angled trapezium plate is height limit part (41), for the plane with the pilot hole of shell (32)
Part cooperates；
Wherein, the emergency release fixation kit (12) includes: locking driving screw rod (39), screw thread compact heap (40), rotation pressure
Tight block (37), screw rod locking cap (38) and rigid pins (36)；One end of locking driving screw rod (39) is equipped with external screw thread, another
End is equipped with tool operation interface；The center of the screw thread compact heap (40) is equipped with threaded hole；
Connection relationship between emergency release fixation kit (12) and rack A main body (18) and rack A seperated (11) are as follows: screw thread pressure
Tight block (40) is fixed in rack A main body (18), and is matched by its threaded hole and the external screw thread of locking driving screw rod (39) one end
It closes；It rotatably compresses block (37) to be fixed on rack A seperated (11) by connection frame, and is fixed on lock by screw rod locking cap (38)
The tool operation interface of the end of thread of tight driving screw rod (39), locking driving screw rod (39) protrudes from the side of bottom plate (2)；Screw thread
Compact heap (40) with rotatably compress block (37) and connect by rigid pins (36)；
Emergency release fixation kit (12) uses and rack A main body (18) and the identical connection type of rack A seperated (11) and machine
Frame B main body (20) is connected with rack B seperated (9).
2. a kind of space load butt-joint locking as described in claim 1 and emergency unlock interface arrangement, which is characterized in that main
Moved end further includes microswitch (1), and microswitch (1) is mounted on the side of bottom plate (2), and the triggering face of microswitch (1) with
The upper surface of drive end is concordant, for monitoring the docking surface contact state of drive end and Partner, when drive end and Partner
It when docking face contact, triggers microswitch (1), shows that drive end and Partner complete docking.
3. a kind of space load butt-joint locking as described in claim 1 and emergency unlock interface arrangement, which is characterized in that two
A master positioning pin (3) and two bulb shear pins (4) are symmetrically distributed in the two sides of lead screw (14) respectively.
4. a kind of space load butt-joint locking as described in claim 1 and emergency unlock interface arrangement, which is characterized in that institute
Master positioning pin (3) is stated to be made of cylindrical section and tip；
The master positioning hole (23) is made of bellmouth and cylindrical hole two parts, and wherein bellmouth is used for and master positioning pin (3)
Tip cooperation, cylindrical hole are used to cooperate with the cylindrical section of master positioning pin (3).
5. a kind of space load butt-joint locking as described in claim 1 and emergency unlock interface arrangement, which is characterized in that institute
Stating drive end further includes blind-mating connector plug (19), and two blind-mating connector plugs (19) are fixed on bottom plate (2), and symmetrical
It is distributed in the two sides of rack A main body (18)；The Partner further includes blind-mating connector socket (27), blind-mating connector socket
(27) it is mounted on framework (26), when Partner is docked with drive end, for being connect with blind-mating connector plug (19).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710139641.9A CN106945852B (en) | 2017-03-09 | 2017-03-09 | A kind of space load butt-joint locking and unlock interface arrangement of meeting an urgent need |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710139641.9A CN106945852B (en) | 2017-03-09 | 2017-03-09 | A kind of space load butt-joint locking and unlock interface arrangement of meeting an urgent need |
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| Publication Number | Publication Date |
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| CN106945852A CN106945852A (en) | 2017-07-14 |
| CN106945852B true CN106945852B (en) | 2019-04-05 |
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| CN201710139641.9A Active CN106945852B (en) | 2017-03-09 | 2017-03-09 | A kind of space load butt-joint locking and unlock interface arrangement of meeting an urgent need |
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Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107628278A (en) * | 2017-07-31 | 2018-01-26 | 北京空间飞行器总体设计部 | With the autonomous in-orbit replaceable units being oriented to linkage function |
| CN108725850B (en) * | 2018-07-02 | 2020-09-18 | 北京控制工程研究所 | Space butt joint locking mechanism |
| CN109703790A (en) * | 2018-12-11 | 2019-05-03 | 兰州空间技术物理研究所 | A kind of four directions bevel-type butt-joint locking device |
| CN110416775B (en) * | 2019-06-03 | 2020-12-08 | 中国航天时代电子有限公司 | Electromechanical butt joint interface and on-orbit reconfigurable aircraft unit based on same |
| CN111169660A (en) * | 2019-12-12 | 2020-05-19 | 北京空间技术研制试验中心 | Exposed load support system for spacecraft |
| CN110884697A (en) * | 2019-12-12 | 2020-03-17 | 北京空间技术研制试验中心 | Extravehicular load interface supporting device |
| CN111071499B (en) * | 2019-12-31 | 2021-06-22 | 中国科学院空间应用工程与技术中心 | Material cabin external exposure device |
| CN112141370A (en) * | 2020-09-04 | 2020-12-29 | 中国空间技术研究院 | Connecting interface between module and cabin section |
| CN115447809B (en) * | 2022-10-31 | 2023-02-24 | 中国人民解放军战略支援部队航天工程大学 | Rendezvous and docking device for multi-body allosteric satellite |
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| US6315247B1 (en) * | 1999-08-05 | 2001-11-13 | Trw Inc. | Spacecraft with a microdynamic noise-free holding mechanism |
| JP2003212199A (en) * | 2002-01-18 | 2003-07-30 | Ishikawajima Harima Heavy Ind Co Ltd | Fixing/separating/capturing device for module |
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| CN106945852A (en) | 2017-07-14 |
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